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|Pegasus SSTO - Pegasus SSTO Launch Vehicle|
Credit: © Mark Wade. 3,664 bytes. 254 x 375 pixels.
Family: VTOVL. Country: USA. Status: Study 1966.
Bono design for semi-single-stage-to-orbit ballistic VTOVL launch vehicle. Drop tanks were shed on the way to orbit. Pegasus could deliver either a Satun V-size payload to LEO or 172 passengers and their luggage the 12,000 km from Vandenberg to Singapore in 39 minutes.
LEO Payload: 90,800 kg. to: 560 km Orbit. at: 28.0 degrees. Liftoff Thrust: 1,910,000 kgf. Total Mass: 1,520,000 kg. Core Diameter: 15.2 m. Total Length: 34.8 m. Total Development Built: 3000. Total Production Built: 1966. Flyaway Unit Cost $: 30.00 million. in 1966 unit dollars. Cost comments: Costs as calculated by Bono. Flyaway cost is average for 48 - first unit would be $ 63 million.
- Stage Number: 0. 8 x Pegasus Tanks Gross Mass: 20,000 kg. Empty Mass: 3,700 kg. Thrust (vac): 0 kgf. Isp: 459 sec. Burn time: 130 sec. Isp(sl): 359 sec. Diameter: 4.6 m. Span: 4.6 m. Length: 18.9 m. Propellants: Lox/LH2 No Engines: 0. None
- Stage Number: 1. 1 x Pegasus VTOVL Gross Mass: 1,250,000 kg. Empty Mass: 148,000 kg. Thrust (vac): 2,442,000 kgf. Isp: 459 sec. Burn time: 360 sec. Isp(sl): 359 sec. Diameter: 10.0 m. Span: 15.2 m. Length: 34.8 m. Propellants: Lox/LH2 No Engines: 1. Plug-Nozzle Pegasus
- 36 - Gatland, Kenneth and Bono, Philip, Frontiers of Space, Macmillan, New York, 1969.
|Pegasus SSTO - Pegasus SSTO Launch Vehicle Cutaway|
Credit: © Mark Wade. 6,213 bytes. 531 x 377 pixels.
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Last update 12 March 2001.
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